Systems and methods for restricting power to a load to prevent engaging circuit protection device for an aircraft

ABSTRACT

A system for restricting power to a load to prevent engaging circuit protection device for an aircraft. The system includes an energy source of an aircraft. The system further includes a plurality of sensors configured to sense at least an electrical parameter of a load of the plurality of loads. The system further includes an aircraft controller configured to receive electrical parameter of a load of the plurality of loads from the plurality of sensors, compare the electrical parameter to at least a current allocation threshold, detect that the electrical parameter has reached the current allocation threshold, calculate a power reduction to the load, and reduce power from the at least an energy source to each load of the plurality of loads by the power reduction. The system further includes at least an electrical circuit of an aircraft, wherein the electrical circuit comprises a circuit protection device.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. Nonprovisional application Ser. No. 16/590,496 filed on Oct. 2, 2019, and entitled, “SYSTEMS AND METHODS FOR ALLOCATING POWER TO A LOAD TO PREVENT ENGAGING CIRCUIT DEVICE PROTECTION”, which claims the benefit of priority of U.S. Provisional Patent Application Ser. No. 62/896,184, filed on Sep. 5, 2019, and titled “SYSTEMS AND METHODS FOR ALLOCATING POWER TO A LOAD TO PREVENT ENGAGING CIRCUIT DEVICE PROTECTION,” which is incorporated by reference herein in its entirety.

FIELD OF THE INVENTION

The present invention generally relates to the field of current allocation in an electric aircraft. In particular, the present invention is directed to systems and methods for restricting power to a load to prevent engaging circuit protection device for an aircraft.

BACKGROUND

During flight, an electric aircraft will utilize energy and power from an onboard energy source. Multiple loads may cause significant stress on the energy source, which may cause a circuit protection device to be engaged to protect the whole electrical power system from overload currents, or other damaging events. Engaging a circuit protection device can result in a loss of electrical feed to a critical aircraft component by disconnecting an energy source, leading to detrimental safety and aircraft functionality concerns. Historically, the means of protecting a circuit protection device have varying levels of efficiency, reusability, weight, and require external control. The need for a means of minimizing a circuit protection device from engaging and causing electrical faults to the subsequent subsystems may be met by restricting power to a load to prevent engaging a circuit protection device for an aircraft. The latter solution can be particularly attractive when an electric aircraft has a constant, intermittent, or occasional need for rotor-based flight, such as may be the case for an aircraft that takes off and/or lands vertically or may need to hover at certain points in the aircraft's flight.

SUMMARY OF THE DISCLOSURE

In one aspect, a system for restricting power to a load to prevent engaging circuit protection device for an aircraft. The further system comprising at least an energy source of an aircraft, wherein the at least an energy source is communicatively coupled to a load of the plurality of loads. The system further comprising a plurality of sensors mounted on the aircraft, wherein each sensor of the plurality of sensors are designed and configured to sense at least an electrical parameter of a load of the plurality of loads. The system further comprising an aircraft controller communicatively connected to the at least an energy source. The aircraft controller is designed and configured to receive at least an electrical parameter of a load of the plurality of loads from the plurality of sensors. The aircraft controller is further designed and configured to compare the at least an electrical parameter to at least a current allocation threshold, wherein the current allocation threshold is generated as a function of at least a circuit protection threshold of load. The aircraft controller is further designed and configured to detect that the at least an electrical parameter has reached the current allocation threshold. The aircraft controller is further designed and configured to calculate a power reduction to the load. The aircraft controller is further designed and configured to reduce power from the at least an energy source to each load of the plurality of loads by the power reduction. The system further includes at least an electrical circuit of an aircraft. The at least an electrical circuit comprises a circuit protection device communicatively connected to the aircraft controller.

In another aspect, a method of restricting power to a load to prevent engaging a circuit protection device for an aircraft. The method comprises sensing, by a plurality of sensors, at least an electrical parameter of a load of the plurality of loads. The method further comprises receiving, by an aircraft controller communicatively connected to at least an energy source, at least an electrical parameter of a load of the plurality of loads from the plurality of sensors. The method further comprises comparing the at least an electrical parameter to at least a current allocation threshold, wherein the current allocation threshold is generated as a function of at least a circuit protection threshold of load. The method further comprises detecting the at least an electrical parameter has reached the current allocation threshold. The method further comprises calculating a power reduction to the load. The method further comprises reducing power from the at least an energy source to each load of the plurality of loads by the power reduction.

These and other aspects and features of non-limiting embodiments of the present invention will become apparent to those skilled in the art upon review of the following description of specific non-limiting embodiments of the invention in conjunction with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

For the purpose of illustrating the invention, the drawings show aspects of one or more embodiments of the invention. However, it should be understood that the present invention is not limited to the precise arrangements and instrumentalities shown in the drawings, wherein:

FIG. 1 is a high-level block diagram illustrating an exemplary embodiment of a circuit diagram within an electric power system;

FIG. 2 is a diagrammatic representation of an electric aircraft;

FIG. 3 is a high-level block diagram depicting an exemplary embodiment of energy source and sensors in an aircraft;

FIGS. 4A-B are schematic diagrams depicting exemplary embodiments of a circuit protection device;

FIG. 5 is a flow chart showing the method of restricting power;

FIGS. 6A-B show electrical parameter measurements over time in relation to threshold limits; and

FIG. 7 is block diagram of a computing system that can be used to implement any one or more of the methodologies disclosed herein and any one or more portions thereof.

The drawings are not necessarily to scale and may be illustrated by phantom lines, diagrammatic representations and fragmentary views. In certain instances, details that are not necessary for an understanding of the embodiments or that render other details difficult to perceive may have been omitted.

DETAILED DESCRIPTION

In the following description, for the purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, that the present invention may be practiced without these specific details. As used herein, the word “exemplary” or “illustrative” means “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” or “illustrative” is not necessarily to be construed as preferred or advantageous over other implementations. All of the implementations described below are exemplary implementations provided to enable persons skilled in the art to make or use the embodiments of the disclosure and are not intended to limit the scope of the disclosure, which is defined by the claims. For purposes of description herein, the terms “upper”, “lower”, “left”, “rear”, “right”, “front”, “vertical”, “horizontal”, and derivatives thereof shall relate to the invention as oriented in FIG. 1. Furthermore, there is no intention to be bound by any expressed or implied theory presented in the preceding technical field, background, brief summary or the following detailed description. It is also to be understood that the specific devices and processes illustrated in the attached drawings, and described in the following specification, are simply exemplary embodiments of the inventive concepts defined in the appended claims. Hence, specific dimensions and other physical characteristics relating to the embodiments disclosed herein are not to be considered as limiting, unless the claims expressly state otherwise.

At a high level, aspects of the present disclosure are directed to systems and methods for restricting the power output to a load to prevent engaging a circuit protection device. Systems for restricting the power output to a load to prevent engaging a circuit protection device in an aircraft may be integrated into any aircraft, electric aircraft, and/or any vertical takeoff and landing aircraft. In an embodiment, a vehicle controller in an electric aircraft will reduce power output to a load, such as a propulsor, if an electrical parameter threatens to reach a threshold which will engage a circuit protection device. Engaging a circuit protection device will disconnect power to critical functions during flight. This novel system may result in, a reduced the risk of engaging the circuit protection device to ensure at least partial power operation for the remaining phases of flight, wherein the plurality of electrical circuits remain functional for the entirety of the flight plan, flight path, and/or remaining phases.

Referring now to the drawings, FIG. 1 illustrates an exemplary embodiment of a system 100 for restricting power to a load to prevent engaging circuit protection device for an aircraft. System 100 for restricting power to a load to prevent engaging circuit protection device for an aircraft includes at least an energy source 104, wherein energy source 104 is driving a plurality of (or at least one) controllable loads 108. At least an energy source 104 may comprise a plurality of energy sources. An energy source of a plurality of energy sources 104 may include, without limitation, a generator, a photovoltaic device, a fuel cell such as a hydrogen fuel cell, direct methanol fuel cell, and/or solid oxide fuel cell, or an electric energy storage device; electric energy storage device may include without limitation a capacitor, an inductor, an energy storage cell and/or a battery. At least an energy source 104 may include a battery cell or a plurality of battery cells connected in series into a module; each module may be connected in series or in parallel with other modules. Configuration of at least an energy source 104 containing connected modules may be designed to meet an energy or power requirement and may be designed to fit within a designated footprint in an electric aircraft in which system 100 may be incorporated. At least an energy source 104 may be used to provide a steady supply of electrical power to a load over the course of a flight by a vehicle or other electric aircraft; the at least an energy source may be capable of providing sufficient power for “cruising” and other relatively low-energy phases of flight. An energy source 104 may be capable of providing electrical power for some higher-power phases of flight as well. At least an energy source of 104 may be capable of providing sufficient electrical power for auxiliary loads, including without limitation lighting, navigation, communications, de-icing, steering or other systems requiring power or energy. At least an energy source 104 may be capable of providing sufficient power for controlled descent and landing protocols, including without limitation hovering descent or conventional runway landing.

Still referring to FIG. 1, at least an energy source 104 may include a device for which power that may be produced per unit of volume and/or mass has been optimized, at the expense of the maximal total specific energy density or power capacity, during design. Non-limiting examples of items that may be used as at least an energy source 104 may include batteries used for starting applications including Li ion batteries which may include NCA, NMC, Lithium iron phosphate (LiFePO4) and Lithium Manganese Oxide (LMO) batteries, which may be mixed with another cathode chemistry to provide more specific power if the application requires Li metal batteries, which have a lithium metal anode that provides high power on demand, Li ion batteries that have a silicon, tin nanocrystals, graphite, graphene or titanate anode, or the like. Batteries may include without limitation batteries using nickel-based chemistries such as nickel cadmium or nickel metal hydride, batteries using lithium ion battery chemistries such as a nickel cobalt aluminum (NCA), nickel manganese cobalt (NMC), lithium iron phosphate (LiFePO4), lithium cobalt oxide (LCO), and/or lithium manganese oxide (LMO), batteries using lithium polymer technology, metal-air batteries. At least an energy source 104 may include lead-based batteries such as without limitation lead acid batteries and lead carbon batteries. At least an energy source 104 may include lithium sulfur batteries, magnesium ion batteries, and/or sodium ion batteries. Batteries may include solid state batteries or supercapacitors or another suitable energy source. Batteries may be primary or secondary or a combination of both. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various devices of components that may be used as at least energy source 104. At least an energy source 104 may be used, in an embodiment, to provide electrical power to an electric aircraft or drone, such as an electric aircraft vehicle, during moments requiring high rates of power output, including without limitation takeoff, landing, thermal de-icing and situations requiring greater power output for reasons of stability, such as high turbulence situations, as described in further detail below.

Still referring to FIG. 1, in an embodiment, at least an energy source 104 may be used to provide a steady supply of electrical power to a critical functions over the course of a flight by an electronic vertical takeoff and landing (eVTOL) vehicle, defined as an electronic vehicle that can take off or land in a vertical or near vertical trajectory, such as rotor-based “hover” takeoff and landing, or the like, or other electric aircraft; the at least an energy source 104 may be capable of providing sufficient power for “cruising” and other relatively low-energy phases of flight. At least an energy source 104 may be capable of providing electrical power for some higher-power phases of flight as well, particularly when high specific energy density energy source is at a high state of charge, as may be the case for instance during takeoff. At least an energy source 104 may be capable of providing sufficient electrical power for auxiliary loads including without limitation, lighting, navigation, communications, de-icing, steering or other systems requiring power or energy. Persons skilled in the art will be aware, after reviewing the entirety of this disclosure, of many different potential components of at least an energy source 104, of a plurality of energy sources.

Continuing to refer to FIG. 1, at least an energy source 104 may supply power to a plurality of critical functions in the aircraft. Critical functions in the aircraft may include, without limitation, communications, flight control, lighting, emergency lighting, heating, navigation, de-icing, steering cruising, landing and descents. Critical functions refer to functions is requisite for safe operation on the aircraft. Critical functions may need to be in operation at all times during flight, even in emergency situations. Noncritical functions have no effect on the safe flight of the aircraft during various phases of flight. These functions can be firstly shed when any reduction in power from the energy source is necessary or there is an emergency situation where power and energy must be allocated elsewhere. High peak loads may be necessary to perform certain landing protocols which may include, but are not limited to, hovering descent or runway descents. During landing, propulsors may demand a higher power than cruising as required to descend in a controlled manner. High peak loads may be necessary to perform certain landing protocols which may include, but are not limited to, hovering descent or runway descents. During landing, propulsors may demand a higher power than cruising as required to descend in a controlled manner.

Continuing to refer to FIG. 1, at least an energy source 104 is electrically connected to a plurality of loads 108. Plurality of loads 108 may include any device or component that consumes electrical power. Plurality of loads 108 may include one or more propulsive devices, including without limitation one or more propellers, turbines, impellers, or other devices for propulsion during flight. Plurality of loads 108 may be, without limitation, in the form of a plurality of propulsive devices. A propulsive device, as described herein, is a component or device used to propel a craft by exerting force on a fluid medium, which may include a gaseous medium such as air or a liquid medium such as water. A propulsive device, as described herein, may include, without limitation, at least a thrust element. At least a thrust element may include any device or component that converts the mechanical energy of a motor, for instance in the form of rotational motion of a shaft, into thrust in a fluid medium. At least a thrust element may include, without limitation, a device using moving or rotating foils, including without limitation one or more rotors, an airscrew or propeller, a set of airscrews or propellers such as contra-rotating propellers, a moving or flapping wing, or the like. At least a thrust element may include without limitation a marine propeller or screw, an impeller, a turbine, a pump-jet, a paddle or paddle-based device, or the like.

With continued reference to FIG. 1, plurality of loads 108 may convert electrical energy into kinetic energy; for instance, first plurality of loads 108 may include one or more electric motors. An electric motor, as described herein, is a device that converts electrical energy into mechanical energy, for instance by causing a shaft to rotate. An electric motor may be driven by direct current (DC) electric power. As an example and without limitation, an electric motor may include a brushed DC electric motor or the like. An electric motor may be, without limitation, driven by electric power having varying or reversing voltage levels, such as alternating current (AC) power as produced by an alternating current generator and/or inverter, or otherwise varying power, such as produced by a switching power source. An electric motor may include, for example and without limitation, brushless DC electric motors, permanent magnet synchronous an electric motor, switched reluctance motors, or induction motors. In addition to inverter and/or a switching power source, a circuit driving an electric motor may include electronic speed controllers (not shown) or other components for regulating motor speed, rotation direction, and/or dynamic braking.

Still referring to FIG. 1, the plurality of loads 108 may, for example and without limitation, convert electrical energy into heat. As a further example and without limitation, plurality of loads 108 may include resistive loads. As another non-limiting example, plurality of loads 108 may convert electrical energy into light. Plurality of loads 108 may include one or more elements of digital or analog circuitry. For example and without limitation, plurality of loads 108 may consume power in the form of voltage sources to provide a digital circuit's high and low voltage threshold levels, to enable amplification by providing “rail” voltages, or the like. Plurality of loads 108 may include, as a non-limiting example, control circuits, aircraft controllers and/or flight controllers as described in further detail below. At least an energy source 104 may connect to a first load of plurality of loads 108 using an electrical connection enabling electrical or electromagnetic power transmission, including any conductive path from high specific energy density energy source device to first load, any inductive, optical or other power coupling such as an isolated power coupling, or any other device or connection usable to convey electrical energy from an electrical power, voltage, or current source. The electrical connection may include, without limitation, a distribution bus. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various devices that may be used as at least the plurality of loads 108.

With continuing reference to FIG. 1, system 100 includes at least an aircraft controller 112. Aircraft controller 112 may include and/or communicate with any computing device as described in this disclosure, including without limitation a microcontroller, microprocessor, digital signal processor (DSP) and/or system on a chip (SoC) as described in this disclosure. Aircraft controller 112 may be installed in an aircraft, may control the aircraft remotely, and/or may include an element installed in the aircraft and a remote element in communication therewith. Aircraft controller 112 may include, be included in, and/or communicate with a mobile device such as a mobile telephone or smartphone. Aircraft controller 112 may include a single computing device operating independently, or may include two or more computing device operating in concert, in parallel, sequentially or the like; two or more computing devices may be included together in a single computing device or in two or more computing devices. Aircraft controller 112 with one or more additional devices as described below in further detail via a network interface device. Network interface device may be utilized for connecting an aircraft controller 112 to one or more of a variety of networks, and one or more devices. Examples of a network interface device include, but are not limited to, a network interface card (e.g., a mobile network interface card, a LAN card), a modem, and any combination thereof. Examples of a network include, but are not limited to, a wide area network (e.g., the Internet, an enterprise network), a local area network (e.g., a network associated with an office, a building, a campus or other relatively small geographic space), a telephone network, a data network associated with a telephone/voice provider (e.g., a mobile communications provider data and/or voice network), a direct connection between two computing devices, and any combinations thereof. A network may employ a wired and/or a wireless mode of communication. In general, any network topology may be used. Information (e.g., data, software etc.) may be communicated to and/or from a computer and/or a computing device. Aircraft controller 112 may include but is not limited to, for example, an aircraft controller 112 or cluster of computing devices in a first location and a second computing device or cluster of computing devices in a second location. Aircraft controller 112 may include one or more computing devices dedicated to data storage, security, distribution of traffic for load balancing, and the like. Aircraft controller 112 may distribute one or more computing tasks as described below across a plurality of computing devices of computing device, which may operate in parallel, in series, redundantly, or in any other manner used for distribution of tasks or memory between computing devices. Aircraft controller 112 may be implemented using a “shared nothing” architecture in which data is cached at the worker, in an embodiment, this may enable scalability of system 100 and/or computing device.

Still referring to FIG. 1, at least an aircraft controller 112 is in communication with the at least an energy source 104 of a plurality of energy sources and the at least a load 108 of the plurality of loads. At least an aircraft controller 112 may be communicatively connected to the at least an energy source 104 of a plurality of energy sources and the at least a load 108 of the plurality of loads. As used herein, “communicatively connecting” is a process whereby one device, component, or circuit is able to receive data from and/or transmit data to another device, component, or circuit; communicative connection may be performed by wired or wireless electronic communication, either directly or by way of one or more intervening devices or components. In an embodiment, communicative connecting includes electrically coupling at least an output of one device, component, or circuit to at least an input of another device, component, or circuit. Communicative connecting may be performed via a bus or other facility for intercommunication between elements of a computing device as described in further detail below in reference to FIG. 7. Communicative connecting may include indirect connections via “wireless” connection, radio communication, low power wide area network, optical communication, magnetic, capacitive, or optical coupling, or the like. Aircraft controller 112 may include any computing device or combination of computing devices as described in detail below in reference to FIG. 7. Aircraft controller 112 may include any processor or combination of processors as described below in reference to FIG. 7. Aircraft controller 112 may include a microcontroller. Aircraft controller 112 may be incorporated in the electric aircraft or may be in remote contact.

Still referring to FIG. 1, aircraft controller 112 may be communicatively connected, as defined above, to each load 108 of plurality of loads; as used herein, aircraft controller 112 is communicatively connected to each load where aircraft controller 112 is able to transmit signals to each load and each load is configured to modify an aspect of load behavior in response to the signals. As a non-limiting example, aircraft controller 112 may transmit signals to load 108, of plurality of loads, via an electrical circuit connecting aircraft controller 112 to the load 108, of a plurality of loads. As an example and without limitation, the circuit may include a direct conductive path from aircraft controller 112 to load or may include an isolated coupling such as an optical or inductive coupling. Alternatively or additionally, aircraft controller 112 may communicate with load 108, of a plurality of loads, using wireless communication, such as without limitation communication performed using electromagnetic radiation including optical and/or radio communication, or communication via magnetic or capacitive coupling. Persons skilled in the art will be aware, after reviewing the entirety of this disclosure, of many different forms and protocols of communication that may be used to communicatively couple aircraft controller 112 to a load 108 of plurality of loads.

In an embodiment and still referring to FIG. 1, aircraft controller 112 may include a reconfigurable hardware platform. A “reconfigurable hardware platform,” as used herein, is a component and/or unit of hardware that may be reprogrammed, such that, for instance, a data path between elements such as logic gates or other digital circuit elements may be modified to change an algorithm, state, logical sequence, or the like of the component and/or unit. This may be accomplished with such flexible high-speed computing fabrics as field-programmable gate arrays (FPGAs), which may include a grid of interconnected logic gates, connections between which may be severed and/or restored to program in modified logic. Reconfigurable hardware platform may be reconfigured to enact any algorithm and/or algorithm selection process received from another computing device and/or created using machine-learning and/or neural net processes as described below.

Still referring to FIG. 1, aircraft controller 112 may be communicatively connected to at least a sensor 116. Sensors, as described herein, are any device, module, and/or subsystems, utilizing any hardware, software, and/or any combination thereof to detect events and/or changes in the instant environment and communicate the information to the at least an aircraft controller. Sensors 116 may be used to monitor the status of the system of both critical and non-critical functions. At least a sensor 116 may be incorporated into vehicle or aircraft or be remote. As an example and without limitation, at least a sensor 116 may be configured to detect the at least an electrical parameter. Electrical parameters may include, without limitation, voltage, current, impedance, resistance, temperature. As an example and without limitation, current may be measured by using a sense resistor in series with the circuit and measuring the voltage drop across the resister, or any other suitable instrumentation and/or methods for detection and/or measurement of current. As a further example and without limitation, voltage may be measured using any suitable instrumentation or method for measurement of voltage, including methods for estimation as described in further detail below. Each of resistance, current, and voltage may alternatively or additionally be calculated using one or more relations between impedance and/or resistance, voltage, and current, for instantaneous, steady-state, variable, periodic, or other functions of voltage, current, resistance, and/or impedance, including without limitation Ohm's law and various other functions relating impedance, resistance, voltage, and current with regard to capacitance, inductance, and other circuit properties. Alternatively, or additionally, aircraft controller 112 may be wired to at least an energy source 104 via, for instance, a wired electrical connection. Measuring at least an electrical parameter may include calculating an electrical parameter based on other sensed electrical parameters, for instance by using Ohm's law to calculate resistance and/or impedance from detected voltage and current levels. Aircraft controller 112 may sense a temperature, environmental parameter, a location parameter, a barometric pressure, or other necessary measurement. Aircraft controller 112 may measure resistance across a circuit via direct method or by calculation. This may be accomplished, for instance, using an analog-to-digital converter, one or more comparators, or any other components usable to measure electrical parameters using an electrical connection that may occur to any person skilled in the art upon reviewing the entirety of this disclosure. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various ways to monitor the status of the system of both critical and non-critical functions.

With continued reference to FIG. 1, aircraft controller 112 may be configured to receive at least an electrical parameter of a load 108 of the plurality of loads from each sensor 116 of the plurality of sensors. At least an electrical parameter of a load 108 is any electrical parameter, as described above. Aircraft controller 112 may be further configured to compare at least an electrical parameter to a current allocation threshold. Comparing may include, without limitation, periodic comparison, continuous comparison, and any combination thereof. Current allocation threshold may be the value at which the aircraft controller 112 will recalculate and redistribute power to the plurality of loads 108, for instance as set forth in the disclosure below. Current allocation threshold may be generated as a function of at least a circuit protection threshold; for instance and without limitation, the current allocation limit may be a set reduction, increase, percentage or other calculation method of the circuit detection limit. Current allocation threshold may include a current threshold, a voltage threshold, a resistance threshold, a temperature threshold, or the like. Current allocation threshold may be derived from in flight data, from manufacturer data, form integrator data, or the like. As a non-limiting example, where a circuit protection device threshold is at 20 A, a corresponding load current allocation threshold limit may be set at 15 A. In another non-limiting example, when measuring voltage, a circuit under voltage protection device threshold may be set at 3V and a corresponding load under potential allocation threshold may be set at 4V. Continuously comparing may include, without limitation, periodic comparisons, such as comparisons performed every second, minute, another pre-determined time or any repeated measurement done at particular time intervals. As a further non-limiting example, aircraft controller 112 may also compare at a predetermined time, or in response to a condition which makes another measurement necessary. In an exemplary embodiment, and for the purposes of illustration, current levels may be measured every 5 milli-seconds until the measurements are within 0.5 A of a current allocation threshold limit at which time the current may be measured every 1 milli-second until the measurement reaches the current allocation threshold. Aircraft controller 112 may compare more than one electrical parameter to a threshold during the segment of flight. In an embodiment and without limitation, aircraft controller 112 may continuously measure current in an energy source 104 or in a plurality of loads 108. Aircraft controller 112 may continuously calculate a greater of a previous two measurements and compare to a graph or other mapping showing the measurements vs time and vs a threshold limit. In an embodiment and without limitation, aircraft controller 112 will compare the electrical parameter measurements to a current allocation threshold which is a fraction of the threshold limit which engages the circuit protection device.

Still referring to FIG. 1, aircraft controller 112 may be further configured to detect the at least an electrical parameter has reached the current allocation threshold may be performed by the controller, computer, remote device or by a person. Detection may, as an example and without limitation, be done by using a direct comparison to determine if the at least an electrical parameter has reached the current allocation threshold. For instance, detection may occur where controller 112 measures a current of 5 A and the current allocation threshold is 5 A. Detection may, as a further non-limiting example, involve the use of calculations or formulas to determine if the current allocation threshold is or has been reached. As another example and without limitation, detecting may be performed by graphing and/or mapping the at least an electrical parameter versus time to determine if the current allocation threshold is reached. Graphing and/or mapping may be coupled with an averaging algorithm if a momentarily high or low datum transiently exceeds current allocation threshold; low-pass filtering of at least an electrical parameter may alternatively or additionally be used to eliminate transient values from comparison. Graphing and/or mapping may be also be combined with a noise reducing algorithm to further process datum. As a further example and without limitation, detection may be performed by calculating a rate of change of at least an electrical parameter, for instance by taking multiple measurements and using differences between measurements to calculate or identify a rate or change. Rate of change of any electrical parameter may be used to calculate and/or predict future electrical parameters at a given or future point in time. Detection may, as a further example and without limitation, involve comparison to a reference chart or another calculation. In an embodiment, detection includes continuously comparing the first electrical parameter to a first current allocation threshold of the at least a current allocation threshold and continuously comparing a second electrical parameter to a second current allocation threshold.

Continuing to refer to FIG. 1, aircraft controller 112 may be further configured to calculate a power reduction to each load 108 of the plurality of loads. The power reduction calculated to at least a load includes using the current allocation threshold limit, the at least an electrical parameter which, in aggregate, will continue to keep the at least an electrical parameter that is sensed below the current allocation threshold. The power reduction calculation may include more than on electrical parameter, a comparison to a graph or other calculated data set, such as a table. In an embodiment, the current allocation calculation assuming a set percentage offset of the current allocation threshold and calculated the aggregate power demand of at least a plurality of loads 108. In another embodiment, aircraft controller 112 calculated a set reduction to each load, of at least a plurality of loads 108 and then calculated the aggregate and compares that value to the current allocation threshold.

Still referring to FIG. 1, the minimum power needed may be used to determine a power reduction for the phase of flight. The calculation may use manufacturing data or data collected by a plurality of sensors during flight. Using the minimum power demand for a particular phase of flight, aircraft controller 112 may determine the total power demand for the plurality of loads by using the power demand of an individual propulsor and multiplying that by the number of loads. In an embodiment and without limitation, aircraft controller 112 may determine if there is enough power in the plurality of energy sources to power the phase of flight and the rest of the flight plan. If there is enough power, aircraft controller 112 may continue to communicate the original flight plan. If there in not adequate power, aircraft controller 112 may reduce the power demand by restricting remaining power output of the plurality of energy sources to one or more motors connected to a propulsor of a plurality of propulsors by communications to the motor supplying power to the plurality of propulsors. As a further example and without limitation, aircraft controller 112 may perform a thrust and/or balance operation to determine if the balance of the aircraft, as a result of the reduced power levels, is operating in a safe range. As another example and without limitation, aircraft controller 112 may detect environmental parameters, using an environmental sensor, which may include, without limitation, wind speed, barometric pressure, humidity and air temperature. Aircraft controller 112 may use at least an environmental parameter to calculate power reduction. In an embodiment, the power reduction of electric aircraft 200 may be a function of the wind speed. The greater the wind speed in opposing the trajectory of electric aircraft 200, the greater the propulsor power needed

With continuing reference to FIG. 1, aircraft controller 112 may further include reducing power from the at least an energy source to each load 108 of the plurality of loads by the power reduction. Reducing power from the at least an energy source 104 to each load of the plurality of loads may include disconnecting the communication between the at least an energy source 104 and the at least an electrical circuit 124. Reducing power from the at least an energy source 104 to each load of the plurality of loads may further include reconnecting the communication between the at least an energy source 104 and the at least an electrical circuit 124. Reducing power from the at least an energy source 104 to each load of the plurality of loads may further include preventing communication between the at least an energy source 104 and the at least an electrical circuit 124. In an embodiment and without limitation, aircraft controller 112 may direct a power reduction to a load 108, of a plurality of loads of an electric aircraft. As a further example and without limitation, aircraft controller 112 may direct the aircraft to change to a flight trajectory which requires reduced power demands. Aircraft controller 112 may generate and/or store a number of predetermined flight trajectories. As another example and without limitation, aircraft controller 112 may calculate and/or store a range of suitable flight trajectories ranked by power demand for a particular flight phase or for the entire flight phase, or both. As a further non-limiting example, aircraft controller 112 may select a top ranked flight trajectory for phase of flight or the entire flight. As another example and without limitation, aircraft controller 112 may select a different flight trajectory for each flight phase. Aircraft controller 112 may, as a non-limiting example, select more than one flight trajectory and communicate to a remote device or person for consideration. One or more flight trajectories may include a combination of geospatial coordinates, a series of waypoints, altitude assignments, and/or time assignments. One or more flight trajectories may include, without limitation, a straight flight course occurring at the same altitude, a spiral flight course which includes turns, a combination of both or a reduction in altitude. In an embodiment and without limitation, aircraft controller 112 may reduce one or more propulsors to operate at a reduced power level that make the aircraft unbalanced and operate in a corkscrew pattern to cruise and or land safely.

With continued reference to FIG. 1, system 100 includes at least an electrical circuit 124. Electrical circuit 124 may be communicatively connected to aircraft controller 112, each load 108 of the plurality of loads, and/or each energy source 104 of the plurality of energy sources. Electrical circuit, as described herein, are any device, module, and/or subsystems, utilizing any hardware, software, and/or any combination thereof to form a path in which electrons from a voltage or current source flow. Electrical circuit 124 may include, without limitation, a series circuit, a parallel circuit, or any combination thereof. Electrical circuit 124 may function to facilitate the electrical flow from each energy source 104 of the plurality of energy sources to each load 108 of the plurality of loads.

Referring still to FIG. 1, circuit protection device 120 is incorporated into electrical circuit 124 in system 100. Circuit protection device 120 may be communicatively connected to aircraft controller 112. Circuit protection device 120 may be a device that protects electrical circuit 124 from different electrical faults such as over current and overload. Circuit protection device 120 may function to break or interrupt electrical flow in a circuit in response to at least an electrical parameter which is reaching a predetermined threshold where a limit may pose a serious threat to the integrity of the circuit or of any component or device connected to or incorporated in the circuit. Circuit protection device 120 may interrupt the circuit by tripping open a part of a circuit, which interrupts the current flow. Circuit protection device 120 may be used to minimize distress to the electrical system and hazard to system, an electric aircraft as disclosed below, passengers, and surrounding aircraft in the event of wiring faults or serious malfunctions of the system or connected equipment. As the current measured reaches a current threshold limit, aircraft controller 112 may engage the circuit protection device 120 to stop current flow to reduce the risk of damage to the propulsor, wires, energy source 104 and surrounding equipment in an electric aircraft.

Continuing to refer to FIG. 1, circuit protective device 120 may include, without limitation, an overload relay which is designed to interrupt the flow of current in an electric circuit upon the detection of undesirable current levels over a period of time; such current levels may lead to serious damage to a motor or other equipment when there is excessive heating of the motor windings. Upon detection of an overload condition, overload relay may output a trip command to a circuit opening mechanism such as a contractor, which may disconnect a load of plurality of loads 108 from at least an energy source 104. Circuit protection device 120 may include, as an example and without limitation, an overload relay of a thermal type, which may include a heater element which may heat a metallic or bimetallic strip, when the load current flows through, to deform that strip enough to force a contact open.

Still referring to FIG. 1, circuit protective device 120 may include, without limitation, a fuse. A fuse may be a base element of a circuit protection device including a small conductive material with low resistance that is placed within a circuit; when a current flowing through circuit and/or fuse exceeds a permitted value, which may be due to an overload, short circuit or load mismatch, the excessive current may melt or otherwise damage the conductive material in the fuse and open the circuit. Various materials may be used as a fusible element which include, without limitation, tin, lead silver, bismuth, and other alloys of these materials. Circuit protection device 120, of a plurality of circuit protection devices, may include, without limitation, a current limiter, defined as a device limiting current to a defined value. Circuit protection device 120 may include, without limitation, a limiting resistor. Limiting resistors may be used to protect electrical circuits, including DC, pulse and AC circuits, for instance in situations where starting/initial current is very high, for example starter engine.

With continued reference to FIG. 1, circuit protection device 120 may further include, as a non-limiting example, a circuit breaker. Circuit breakers may differ from fuses and current limiters in that they may include electromechanical devices that interrupt and isolate circuit in case of failure; the working principle may include actuation of the electromechanical device by heating of bi-metallic element through which current passes to the switch unit, or by any other suitable trigger. Circuit protection device 120 may further include, without limitation, a solid-state power controller (SSPC) which may be a semiconductor device that controls power in the form of power, voltage, and/or current which are supplied to a load; such devices may perform supervisory and diagnostic functions in order to identify overload conditions and prevent short circuits. Circuit protection device 120 may include, as a further non-limiting example, a secondary back up protection device, which may include a fuse as described above. For instance, and without limitation, dual-element (two-element) fuse or time delay fuses may provide secondary overload protection. Accordingly, for an example and without limitation, such a fuse may represent a secondary failure and be intended to prevent further operation.

Now referring to FIG. 2, system 100 may be incorporated into an electrically powered aircraft 200. Electrically powered aircraft 200 may be an electric vertical takeoff and landing (eVTOL) aircraft. Electrically powered aircraft 200 may include at least a load 108 of a plurality of loads. Electrically powered aircraft 200 may include an aircraft controller 112 communicatively and/or operatively connected to each load 108. Electrically powered aircraft 200 may be capable of rotor-based cruising flight, rotor-based takeoff, rotor-based landing, fixed-wing cruising flight, airplane-style takeoff, airplane-style landing, and/or any combination thereof. Rotor-based flight, as described herein, is where the aircraft generated lift and propulsion by way of one or more powered rotors coupled with an engine, such as a “quad copter,” multi-rotor helicopter, or other vehicle that maintains its lift primarily using downward thrusting propulsors. Fixed-wing flight, as described herein, is where the aircraft is capable of flight using wings and/or foils that generate life caused by the aircraft's forward airspeed and the shape of the wings and/or foils, such as airplane-style flight.

Continuing to refer to FIG. 2, an illustration of aerodynamic forces is illustrated in an electric aircraft. During flight, a number of aerodynamic forces may act upon the electric aircraft. Forces acting on an aircraft 200 during flight may include thrust, the forward force produced by the rotating element of the aircraft 200 and acts parallel to the longitudinal axis. Drag may be defined as a rearward retarding force which is caused by disruption of airflow by any protruding surface of the aircraft 200 such as, without limitation, the wing, rotor, and fuselage. Drag may oppose thrust and acts rearward parallel to the relative wind. Another force acting on aircraft 200 may include weight, which may include a combined load of the aircraft 200 itself, crew, baggage and fuel. Weight may pull aircraft 200 downward due to the force of gravity. An additional force acting on aircraft 200 may include lift, which may act to oppose the downward force of weight and may be produced by the dynamic effect of air acting on the airfoil and/or downward thrust from at least a propulsor 108. Lift generated by the airfoil may depends on speed of airflow, density of air, total area of an airfoil and/or segment thereof, and/or an angle of attack between air and the airfoil.

Referring now to FIG. 3, a plurality of sensors, each or all of which may act as at least a sensor 116, may be incorporated in system 100. Sensors of plurality of sensors may be designed to measure a plurality of electrical parameters or environmental data in-flight, for instance as described above. Plurality of sensors may, as a non-limiting example, include a voltage sensor 300 designed and configured to measure the voltage of at least an energy source 104, as described above in reference to FIG. 1. As an example and without limitation, the plurality of sensors may include a current sensor 304 designed and configured to measure the current of at least an energy source 104, as described above in reference to FIG. 1. As a further example and without limitation, the plurality of sensors may include a temperature sensor 308 designed and configured to measure the temperature of at least an energy source 104. As another non-limiting example, the plurality of sensors may include a resistance sensor 312 designed and configured to measure the resistance of at least an energy source 104.

Continuing to refer to FIG. 3, the plurality of sensors may include at least an environmental sensor 316. In an embodiment, environmental sensor may sense one or more environmental conditions or parameters outside the electric aircraft, inside the electric aircraft, or within or at any component thereof, including without limitation at least an energy source 104, at least a propulsor, or the like; environmental sensor may include, without limitation, a temperature sensor, a barometric pressure sensor, an air velocity sensor, one or more motion sensors which may include gyroscopes, accelerometers, and/or a inertial measurement unit (IMU), a magnetic sensor, humidity sensor, an oxygen sensor and/or a wind speed sensor. At least a sensor 116 may include at least a geospatial sensor. As used herein, a geospatial sensor may include without limitation optical devices, radar devices, Lidar devices, and/or Global Positioning System (GPS) devices, and may be used to detect aircraft location, aircraft speed, aircraft altitude and/or whether the aircraft is on the correct location of the flight plan. Environmental sensor 432 may be designed and configured to measure geospatial data to determine the location and altitude of the electronically powered aircraft by any location method including, without limitation, GPS, optical, satellite, lidar, radar. Environmental sensor 432 may be designed and configured to measure at a least a parameter of the motor. Environmental sensor 432 may be designed and configured to measure at a least a parameter of the propulsor. Environmental sensor 432 may be configured to measure conditions external to the electrical aircraft 404 such as, without limitation, humidity, altitude, barometric pressure, temperature, noise and/or vibration. Sensor datum collected in flight may be transmitted to the aircraft controller 112 or to a remote device 320, which may be any device, as described below in reference to FIG. 7. As an example and without limitation, remote device 320 may be used to compare the at least an electrical parameter to the at least a current allocation threshold and/or detect that the at least an electrical parameter has reached the current allocation threshold, as described in further detail below.

Now referring to FIG. 4A, circuit protection device 120 is shown in a circuit. Circuit protection device 120 may function in response to a number of electrical events. A short circuit may form where there is a hard short between a high voltage side of a circuit and the ground, return, and/or virtual ground, or the like. Potential hazards resulting from a short circuit may include overheating of wires and subsequent faults as well as damage to equipment (equipment bonding). All protective devices as described above may be designed to respond to a shorting event. An overload condition may occur where the loads in the circuit are pulling more current than the system is designed to handle. As an example and without limitation, a load may draw 20 A of current on a 15 A current resulting in an overload condition. Parallel arcing may also occur where electricity discharges across an insulting medium such as two wires carrying current. As a further example and without limitation, faulty operation of equipment wired in an aircraft or other devices may also cause conditions that may cause a circuit protection device to trip to protect a device. In the circuit, energy source 104 is connected to a load, such as a load of plurality of loads 108. In an embodiment and without limitation, load 108 may include a propulsor in an electric aircraft. During normal operation, current flows within electrical circuit 124 as illustrated in FIG. 4A.

Referring now to FIG. 4B, illustrated is the circuit when circuit protection device 120 is engaged and open. When circuit protection device 120 is engaged, electrical circuit 124 may be open, preventing and stopping current flow from at least an energy source 104 to plurality of loads 108. As an additional example and without limitation, circuit protection device 120 may shunt current away from electrical circuit 124. Engagement of the circuit protection device 120 may, as an example and without limitation, occur upon tripping a threshold, or limit, based on an electrical parameter, which may be any electrical parameter as described above. In an embodiment and without limitation, sensor 116 may measure current draw between an energy source 104 and a plurality of loads 108. At a predetermined circuit protection threshold, aircraft controller 112 may engage circuit protection device 120 to current flow, thus reducing risk of damage to electrical circuit 124 and/or devices or components connected to the electrical circuit 124. Circuit protection threshold, as described herein, may be the maximum allowed current flow and/or voltage flow the electric circuit 124 is able to withstand. As another example and without limitation, circuit protection threshold may be the maximum current flow and/or voltage flow each load 108 of the plurality of loads is able to utilize without negative system impacts. In another embodiment and without limitation, aircraft controller 112 may sense current flow from a propulsor in an electrical aircraft driven by at least an energy source 104.

Now referring to FIG. 5, an exemplary embodiment of method 500 of restricting power to a plurality of loads to prevent engaging a circuit protection device for an aircraft is illustrated. At step 505, each sensor 116 of a plurality of sensors senses an electrical parameter from an electrical circuit 124 which includes at least an energy source 104 driving a plurality of loads 108. Electrical circuit 124 may include a circuit protection device 120. A least an electrical parameter may include any electrical parameter as described above, including without limitation a voltage, current, resistance, temperature or environmental parameter. At least an electrical parameter may be measured, for instance, using any means or method as described above, including using at least a sensor 116 and/or via an electrical or other connection between aircraft controller 112 and at least an energy source 104.

Continuing to refer to FIG. 5, in an embodiment, sensing at least an electrical parameter may include measuring a voltage. Voltage of a battery cell, a plurality of battery cells, modules or plurality of modules may be measured. Voltage under plurality of loads 108 may be alternatively or additionally measured or detected. sensing at least an electrical parameter may include measuring a current; a current of a battery cell, a plurality of battery cells, modules or plurality of modules may be measured. Sensing at least an electrical parameter may include inferring or calculating an electrical parameter based on sensed electrical parameters, for instance by using Ohm's law or other relations as described and/or discussed above to calculate resistance and/or impedance from detected voltage and current levels. At least an electrical parameter may include signal properties such as frequency, wavelength, or amplitude of one or more components of a voltage or current signal. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various electrical parameters, and techniques for measuring such parameters, consistent with this disclosure.

Still referring to FIG. 5 at least an electrical parameter may be a current. At least a sensor 116, of a plurality of sensors may measure current directly or calculate the current given other electrical parameters which include voltage and resistance. Current of any component in energy source 104, such as a cell, battery cells, plurality of battery cells may be measured. Current flow through wires, a plurality of wires, or other electrical components by which current is carried may be measured. Current flowing between two components of system 100 may be measured; the two components may be connected via current carrying wire. In an embodiment, such as where system 100 is in an electric aircraft, wire gauge may be reduced in order to save on weight, which may be critical to the design of the aircraft. When the wire gauge is reduced, the potential for overload of current in the wire with current may rise. Any current flow that is in excess of the current carrying capability of the wire may cause heat, and rapid heat may be caused when a direct short is created. These conditions may engage circuit protection device at a circuit protection device threshold.

Still referring to FIG. 5, at step 510, aircraft controller 112 receives at least an electrical parameter of a load 108 of the plurality of loads from each sensor 116 of the plurality of sensors. At least an electrical parameter of a load 108 is any electrical parameter as described above in reference to FIGS. 1-5. At step 515, aircraft controller 112 compares at least an electrical parameter to a current allocation threshold. Comparing at least an electrical parameter to a current allocation threshold may include periodic comparison, continuous comparison, and any combination thereof. Current allocation threshold may be the value at which the aircraft controller 112 will recalculate and redistribute power to the plurality of loads 108, for instance as set forth in the disclosure below. Current allocation threshold may be generated as a function of at least a circuit protection threshold; for instance and without limitation, the current allocation limit may be a set reduction, increase, percentage or other calculation method of the circuit detection limit. Current allocation threshold may include a current threshold, a voltage threshold, a resistance threshold, a temperature threshold, or the like. Current allocation threshold may be derived from in flight data, from manufacturer data, form integrator data, or the like, as described above in reference to FIG. 1.

Still referring to FIG. 5, at step 520, aircraft controller 112 detects that the at least an electrical parameter has reached the current allocation threshold. Detecting the at least an electrical parameter has reached the current allocation threshold may be performed by the controller, computer, remote device or by a person. Detection may, as an example and without limitation, be done by using a direct comparison to determine if the at least an electrical parameter has reached the current allocation threshold. For instance, detection may occur where controller 112 measures a current of 5 A and the current allocation threshold is 5 A. Detection may, as a further non-limiting example, involve the use of calculations or formulas to determine if the current allocation threshold is or has been reached. As another example and without limitation, detecting may be performed by graphing and/or mapping the at least an electrical parameter versus time to determine if the current allocation threshold is reached. Further examples of aircraft controller 112 detecting the at least an electrical parameter has reached the current allocation threshold are described above in reference to FIG. 1.

Continuing to refer to FIG. 5, at step 525, aircraft controller 112 calculates a power reduction to at least a load of a plurality of loads 108. The power reduction calculated to at least a load includes using the current allocation threshold limit, the at least an electrical parameter which, in aggregate, will continue to keep the at least an electrical parameter that is sensed below the current allocation threshold. The power reduction calculation may include more than on electrical parameter, a comparison to a graph or other calculated data set, such as a table. In an embodiment, the current allocation calculation assuming a set percentage offset of the current allocation threshold and calculated the aggregate power demand of at least a plurality of loads 108. In another embodiment, aircraft controller 112 calculated a set reduction to each load, of at least a plurality of loads 108 and then calculated the aggregate and compares that value to the current allocation threshold.

Still referring to FIG. 5, controller 112 may determine a minimum power demand of plurality of loads 108, which can be a propulsor, of plurality of propulsors, needed for a particular phase of flight using the speed, distance, altitude and the like. The minimum power needed may be used to determine a power reduction for the phase of flight. The calculation may use manufacturing data or data collected by a plurality of sensors during flight. Using the minimum power demand for a particular phase of flight, aircraft controller 112 may determine the total power demand for the plurality of loads by using the power demand of an individual propulsor and multiplying that by the number of loads. Further examples of aircraft controller 112 determining a minimum power demand for each load of the plurality of loads 108 are described above in reference to FIG. 1.

Still referring to FIG. 5, at step 530, aircraft controller 112 reduces power from the at least an energy source 104 to each load of the plurality of loads 108. Reducing power from the at least an energy source 104 to each load of the plurality of loads may include disconnecting the communication between the at least an energy source 104 and the at least an electrical circuit 124, as described above in reference to FIGS. 1-3. Reducing power from the at least an energy source 104 to each load of the plurality of loads may further include reconnecting the communication between the at least an energy source 104 and the at least an electrical circuit 124, as described above in reference to FIGS. 1-3. Reducing power from the at least an energy source 104 to each load of the plurality of loads may further include preventing communication between the at least an energy source 104 and the at least an electrical circuit 124, as described above in reference to FIGS. 1-3. In an embodiment and without limitation, aircraft controller 112 may direct a power reduction to a load 108, of a plurality of loads of an electric aircraft.

Now referring to FIG. 6A-B, FIG. 6A displays a graph showing a graph of exemplary voltage measurements over time of a component. For example and without limitation, a component, as described herein, may include energy source 104, a load of plurality of loads 108, any combination thereof, or the like. Illustrated in FIG. 6A is a current allocation threshold. The current allocation threshold is an upper limit where controller 112 will calculate a power reduction to plurality of loads 108, such that the voltage does not exceed a threshold where the circuit protection device 120 is engaged. As displayed in FIG. 6A, the dotted line demonstrates where power reduction has occurred thus reducing the risk of engaging the circuit protection device 120. FIG. 6B displays a graph showing similar conditions to FIG. 6A. FIG. 6B displays plots of current over time, as opposed to FIG. 6A displaying voltage over time. FIG. 6B demonstrates the point at which controller 112 will reduce the power reduction of a load and the resulting measurements decreasing risk of engaging the circuit protection device 120.

In an embodiment, the above-described elements may alleviate problems resulting from systems wherein a circuit protection device is engaged, and critical functions are denied power. This can compromise the safety of the flight due to the termination of current to a critical function in the aircraft. An in-flight current allocation for the remaining in-flight power output capacity to reduce the risk of engaging a circuit protection device will ensure safe operation for any phase of the flight including taxi, take off, cruise and landing modes. There are other methods which can reduce the risk of engaging a circuit protection device, which includes increasing the wires and current carrying equipment, but this adds weight to the aircraft that is not desirable. Above-described embodiments enable the optimization of power sources in a lightweight and robust configuration compatible with safe and high-performance flight.

It is to be noted that any one or more of the aspects and embodiments described herein may be conveniently implemented using one or more machines (e.g., one or more computing devices that are utilized as a user computing device for an electronic document, one or more server devices, such as a document server, etc.) programmed according to the teachings of the present specification, as will be apparent to those of ordinary skill in the computer art. Appropriate software coding can readily be prepared by skilled programmers based on the teachings of the present disclosure, as will be apparent to those of ordinary skill in the software art. Aspects and implementations discussed above employing software and/or software modules may also include appropriate hardware for assisting in the implementation of the machine executable instructions of the software and/or software module.

Such software may be a computer program product that employs a machine-readable storage medium. A machine-readable storage medium may be any medium that is capable of storing and/or encoding a sequence of instructions for execution by a machine (e.g., a computing device) and that causes the machine to perform any one of the methodologies and/or embodiments described herein. Examples of a machine-readable storage medium include, but are not limited to, a magnetic disk, an optical disc (e.g., CD, CD-R, DVD, DVD-R, etc.), a magneto-optical disk, a read-only memory “ROM” device, a random access memory “RAM” device, a magnetic card, an optical card, a solid-state memory device, an EPROM, an EEPROM, and any combinations thereof. A machine-readable medium, as used herein, is intended to include a single medium as well as a collection of physically separate media, such as, for example, a collection of compact discs or one or more hard disk drives in combination with a computer memory. As used herein, a machine-readable storage medium does not include transitory forms of signal transmission.

Such software may also include information (e.g., data) carried as a data signal on a data carrier, such as a carrier wave. For example, machine-executable information may be included as a data-carrying signal embodied in a data carrier in which the signal encodes a sequence of instruction, or portion thereof, for execution by a machine (e.g., a computing device) and any related information (e.g., data structures and data) that causes the machine to perform any one of the methodologies and/or embodiments described herein.

Examples of a computing device include, but are not limited to, an electronic book reading device, a computer workstation, a terminal computer, a server computer, a handheld device (e.g., a tablet computer, a smartphone, etc.), a web appliance, a network router, a network switch, a network bridge, any machine capable of executing a sequence of instructions that specify an action to be taken by that machine, and any combinations thereof. In one example, a computing device may include and/or be included in a kiosk.

FIG. 7 shows a diagrammatic representation of one embodiment of a computing device in the exemplary form of a computer system 700 within which a set of instructions for causing a control system, such as the system 100 system of FIG. 7, to perform any one or more of the aspects and/or methodologies of the present disclosure may be executed. It is also contemplated that multiple computing devices may be utilized to implement a specially configured set of instructions for causing one or more of the devices to perform any one or more of the aspects and/or methodologies of the present disclosure. Computer system 700 includes a processor 704 and a memory 708 that communicate with each other, and with other components, via a bus 712. Bus 712 may include any of several types of bus structures including, but not limited to, a memory bus, a memory controller, a peripheral bus, a local bus, and any combinations thereof, using any of a variety of bus architectures.

Memory 708 may include various components (e.g., machine-readable media) including, but not limited to, a random-access memory component, a read only component, and any combinations thereof. In one example, a basic input/output system 716 (BIOS), including basic routines that help to transfer information between elements within computer system 700, such as during start-up, may be stored in memory 708. Memory 708 may also include (e.g., stored on one or more machine-readable media) instructions (e.g., software) 720 embodying any one or more of the aspects and/or methodologies of the present disclosure. In another example, memory 708 may further include any number of program modules including, but not limited to, an operating system, one or more application programs, other program modules, program data, and any combinations thereof.

Computer system 700 may also include a storage device 724. Examples of a storage device (e.g., storage device 724) include, but are not limited to, a hard disk drive, a magnetic disk drive, an optical disc drive in combination with an optical medium, a solid-state memory device, and any combinations thereof. Storage device 724 may be connected to bus 712 by an appropriate interface (not shown). Example interfaces include, but are not limited to, SCSI, advanced technology attachment (ATA), serial ATA, universal serial bus (USB), IEEE 1394 (FIREWIRE), and any combinations thereof. In one example, storage device 724 (or one or more components thereof) may be removably interfaced with computer system 700 (e.g., via an external port connector (not shown)). Particularly, storage device 724 and an associated machine-readable medium 728 may provide nonvolatile and/or volatile storage of machine-readable instructions, data structures, program modules, and/or other data for computer system 700. In one example, software 720 may reside, completely or partially, within machine-readable medium 728. In another example, software 720 may reside, completely or partially, within processor 704.

Computer system 700 may also include an input device 732. In one example, a user of computer system 700 may enter commands and/or other information into computer system 700 via input device 732. Examples of an input device 732 include, but are not limited to, an alpha-numeric input device (e.g., a keyboard), a pointing device, a joystick, a gamepad, an audio input device (e.g., a microphone, a voice response system, etc.), a cursor control device (e.g., a mouse), a touchpad, an optical scanner, a video capture device (e.g., a still camera, a video camera), a touchscreen, and any combinations thereof. Input device 732 may be interfaced to bus 712 via any of a variety of interfaces (not shown) including, but not limited to, a serial interface, a parallel interface, a game port, a USB interface, a FIREWIRE interface, a direct interface to bus 712, and any combinations thereof. Input device 732 may include a touch screen interface that may be a part of or separate from display 736, discussed further below. Input device 732 may be utilized as a user selection device for selecting one or more graphical representations in a graphical interface as described above.

A user may also input commands and/or other information to computer system 700 via storage device 724 (e.g., a removable disk drive, a flash drive, etc.) and/or network interface device 740. A network interface device, such as network interface device 740, may be utilized for connecting computer system 700 to one or more of a variety of networks, such as network 744, and one or more remote devices 748 connected thereto. Examples of a network interface device include, but are not limited to, a network interface card (e.g., a mobile network interface card, a LAN card), a modem, and any combination thereof. Examples of a network include, but are not limited to, a wide area network (e.g., the Internet, an enterprise network), a local area network (e.g., a network associated with an office, a building, a campus or other relatively small geographic space), a telephone network, a data network associated with a telephone/voice provider (e.g., a mobile communications provider data and/or voice network), a direct connection between two computing devices, and any combinations thereof. A network, such as network 744, may employ a wired and/or a wireless mode of communication. In general, any network topology may be used. Information (e.g., data, software 720, etc.) may be communicated to and/or from computer system 700 via network interface device 740.

Computer system 700 may further include a video display adapter 752 for communicating a displayable image to a display device, such as display device 736. Examples of a display device include, but are not limited to, a liquid crystal display (LCD), a cathode ray tube (CRT), a plasma display, a light emitting diode (LED) display, and any combinations thereof. Display adapter 752 and display device 736 may be utilized in combination with processor 704 to provide graphical representations of aspects of the present disclosure. In addition to a display device, computer system 700 may include one or more other peripheral output devices including, but not limited to, an audio speaker, a printer, and any combinations thereof. Such peripheral output devices may be connected to bus 712 via a peripheral interface 756. Examples of a peripheral interface include, but are not limited to, a serial port, a USB connection, a FIREWIRE connection, a parallel connection, and any combinations thereof.

The foregoing has been a detailed description of illustrative embodiments of the invention. Various modifications and additions can be made without departing from the spirit and scope of this invention. Features of each of the various embodiments described above may be combined with features of other described embodiments as appropriate in order to provide a multiplicity of feature combinations in associated new embodiments. Furthermore, while the foregoing describes a number of separate embodiments, what has been described herein is merely illustrative of the application of the principles of the present invention. Additionally, although particular methods herein may be illustrated and/or described as being performed in a specific order, the ordering is highly variable within ordinary skill to achieve methods, systems, and software according to the present disclosure. Accordingly, this description is meant to be taken only by way of example, and not to otherwise limit the scope of this invention.

Exemplary embodiments have been disclosed above and illustrated in the accompanying drawings. It will be understood by those skilled in the art that various changes, omissions and additions may be made to that which is specifically disclosed herein without departing from the spirit and scope of the present invention. 

What is claimed is:
 1. A system for restricting power to a load to prevent engaging a circuit protection device for an electric aircraft, the system comprising: at least an energy source of an electric aircraft, wherein the at least an energy source is communicatively coupled to a load of a plurality of loads, wherein the load comprises at least a portion of a propulsion system of the electric aircraft; a plurality of sensors mounted on the electric aircraft, wherein each sensor of the plurality of sensors are designed and configured to: sense at least an electrical parameter of the at least a portion of the propulsion system of the electric aircraft; an aircraft controller communicatively connected to the at least an energy source, wherein the aircraft controller is designed and configured to: receive at least an electrical parameter of the at least a portion of the propulsion system of the electric aircraft from the plurality of sensors; compare the at least an electrical parameter to at least a current allocation threshold, wherein the current allocation threshold is generated as a function of at least a circuit protection threshold of load; detect that the at least an electrical parameter has reached the current allocation threshold; calculate a power reduction to the load; at least an electrical circuit of the electric aircraft, wherein the at least an electrical circuit comprises: a circuit protection device communicatively connected to the aircraft controller.
 2. The system of claim 1, wherein the plurality of sensors further comprises the plurality of sensors communicatively connected to the aircraft controller.
 3. The system of claim 1, wherein the plurality of sensors further includes: at least a current sensor; and at least a voltage sensor.
 4. The system of claim 1, wherein comparing the at least an electrical parameter to the at least a current allocation threshold further comprises: periodic comparison; and continuous comparison.
 5. The system of claim 1, further comprising a user selection device, wherein the user selection device is configured to: receive the power reduction to the load; display the power reduction to the load.
 6. The system of claim 5, wherein the user selection device is further configured to: audibly announce the power reduction to the load.
 7. The system of claim 1, wherein the at least a circuit protection device further includes an overload relay.
 8. The system of claim 1, wherein the at least a circuit protection device further includes: a fuse; and a circuit breaker.
 9. A method of restricting power to a load to prevent engaging a circuit protection device for an electric aircraft, the method comprising: sensing, by a plurality of sensors, at least an electrical parameter of a load of the plurality of loads; receiving, by an aircraft controller communicatively connected to at least an energy source, at least an electrical parameter of at least a portion of the propulsion system of the electric aircraft from the plurality of sensors; comparing the at least an electrical parameter to at least a current allocation threshold, wherein the current allocation threshold is generated as a function of at least a circuit protection threshold of load; detecting the at least an electrical parameter has reached the current allocation threshold; calculating a power reduction to the load.
 10. The method of claim 9, wherein sensing the at least an electrical parameter further comprises sensing, by at least a current sensor, a current level.
 11. The method of claim 9, wherein sensing the at least an electrical parameter further comprises sensing, by at least a voltage sensor, a voltage level.
 12. The method of claim 9, wherein comparing the at least an electrical parameter to the at least a current allocation threshold further comprises: continuously comparing; and periodically comparing.
 13. The method of claim 9, wherein the aircraft controller is configured to: receiving a reduction confirmation datum; and reducing power from the at least an energy source to each load of the plurality of loads by the power reduction as a function of receiving the reduction confirmation datum.
 14. The method of claim 13, wherein reducing power from the at least an energy source to each load further includes: disconnecting the communication between the at least an energy source and the at least an electrical circuit; and reconnecting the communication between the at least an energy source and the at least an electrical circuit.
 15. The method of claim 13, wherein reducing power from the at least an energy source to each load further includes: preventing communication between the at least an energy source and the at least an electrical circuit.
 16. The method of claim 9, further comprising a user selection device, wherein the user selection device is configured to: receiving the power reduction to the load; displaying the power reduction to the load.
 17. The method of claim 16, wherein the user selection device is further configured to: audibly announcing the power reduction to the load. 